Shock tunnel measurements of surface pressures in shock induced separated flow field using MEMS sensor array

Sriram, R.; Ram, Shobha Sundar; Hegde, Gopalkrishna; Nayak, M. M.; Jagadeesh, G.

doi:10.1088/0957-0233/26/9/095301

Cited by 10 publications

(5 citation statements)

References 28 publications

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“…However, shock tunnel simulations are characterized by short run times generally around 1 ms. Surface pressure measurements upto 50,000 Pa using MEMS sensor array at Mach 5.96 and Mach 8.67 were carried out by Sriram et al (2015). With the substantial growth in the MEMS industry over the past 20 years, the concept of multi-sensors over a single chip has emerged.…”

Section: Aerospace Applicationsmentioning

confidence: 99%

A review of principles of MEMS pressure sensing with its aerospace applications

Javed

Mansoor

Shah

2019

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Purpose Pressure, being one of the key variables investigated in scientific and engineering research, requires critical and accurate measurement techniques. With the advancements in materials and machining technologies, there is a large leap in the measurement techniques including the development of micro electromechanical systems (MEMS) sensors. These sensors are one to two orders smaller in magnitude than traditional sensors and combine electrical and mechanical components that are fabricated using integrated circuit batch-processing technologies. MEMS are finding enormous applications in many industrial fields ranging from medical to automotive, communication to electronics, chemical to aviation and many more with a potential market of billions of dollars. MEMS pressure sensors are now widely used devices owing to their intrinsic properties of small size, light weight, low cost, ease of batch fabrication and integration with an electronic circuit. This paper aims to identify and analyze the common pressure sensing techniques and discuss their uses and advantages. As per our understanding, usage of MEMS pressure sensors in the aerospace industry is quite limited due to cost constraints and indirect measurement approaches owing to the inability to locate sensors in harsh environments. The purpose of this study is to summarize the published literature for application of MEMS pressure sensors in the said field. Five broad application areas have been investigated including: propulsion/turbomachinery applications, turbulent flow diagnosis, experimentalaerodynamics, micro-flow control and unmanned aerial vehicle (UAV)/micro aerial vehicle (MAV) applications. Design/methodology/approach The first part of the paper deals with an introduction to MEMS pressure sensors and mathematical relations for its fabrication. The second part covers pressure sensing principles followed by the application of MEMS pressure sensors in five major fields of aerospace industry. Findings In this paper, various pressure sensing principles in MEMS and applications of MEMS technology in the aerospace industry have been reviewed. Five application fields have been investigated including: Propulsion/Turbomachinery applications, turbulent flow diagnosis, experimental aerodynamics, micro-flow control and UAV/MAV applications. Applications of MEMS sensors in the aerospace industry are quite limited due to requirements of very high accuracy, high reliability and harsh environment survivability. However, the potential for growth of this technology is foreseen due to inherent features of MEMS sensors’ being light weight, low cost, ease of batch fabrication and capability of integration with electric circuits. All these advantages are very relevant to the aerospace industry. This work is an endeavor to present a comprehensive review of such MEMS pressure sensors, which are used in the aerospace industry and have been reported in recent literature. Originality/value As per the author’s understanding, usage of MEMS pressure sensors in the aerospace industry is quite limited due to cost constraints and indirect measurement approaches owing to the inability to locate sensors in harsh environments. Present work is a prime effort in summarizing the published literature for application of MEMS pressure sensors in the said field. Five broad application areas have been investigated including: propulsion/turbomachinery applications, turbulent flow diagnosis, experimental aerodynamics, micro-flow control and UAV/MAV applications.

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Section: Aerospace Applicationsmentioning

confidence: 99%

A review of principles of MEMS pressure sensing with its aerospace applications

Javed

Mansoor

Shah

2019

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“…The various diagnostic techniques employed in these facilities are measurements of surface pressure, temperature/heat transfer [6,7], skin friction [8], aerodynamic forces and moments [9], qualitative flow field visualizations using Schlieren/shadowgraph techniques, and density field measurements using interferometry [10][11][12]. Surface pressure measurements are essential for computing aerodynamic drag forces and moments, as well as the unsteadiness of the flow [13].…”

Section: Introductionmentioning

confidence: 99%

“…The selection of suitable pressure sensors depends on range, sensitivity, size, frequency of interest and adaptability in highspeed aerodynamic flow environments. In supersonic flow studies, flush-mounted piezoelectric, piezoresistive, microelectromechanical systems-based pressure sensors [13] and pitot sensing probes have been used for pressure measurement. Pressure sensors currently used for pressure measurements in supersonic flow environments are mostly of the electrical type.…”

Section: Introductionmentioning

confidence: 99%

Simultaneous measurement of pressure and temperature in a supersonic ejector using FBG sensors

Hegde¹,

Himakar²,

V³

et al. 2022

Meas. Sci. Technol.

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In this work, we have demonstrated the use of Fiber Bragg Grating (FBG) sensors for simultaneous measurement of wall static pressure and temperature in a supersonic ejector. Supersonic ejectors are ground based high speed aerodynamic test facilities characterized by harsh conditions such as high pressure and temperature gradients. FBG based sensor setup was developed consisting of pressure measuring bare FBG and specially designed pressure-insensitive FBG temperature probe that could be mounted on the wall of the supersonic ejector. The FBG temperature probe was used for temperature measurement as well as temperature compensation of pressure measuring FBG sensor. Wall static pressure measurements in the supersonic ejector were carried out at different tank pressures and Mach number flows. The FBG pressure measurements were validated with that of standard piezoresistive based sensor measurements. Both the responses were found to match closely with FBG sensor having a faster response time and higher pressure resolution. Fluid structure interaction simulation was carried out in Comsol Multiphysics to understand the interaction of high speed turbulent flow on the fiber based FBG sensor. The FBG strain profile due to flow-induced stress and its dependence on flow pressure was studied. A detailed analysis of effect of preceding fiber length on FBG pressure measurement was carried out. FBG sensors, owing to their miniature size, ability to withstand harsh environments and multi parameter sensing capability can be used in ground-based aerodynamic test facilities with minimum intrusion to the flow.

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“…The ability to sense the measurand over an ultra-short duration is a requirement for any measurement technique used in hypersonic testing [1]. Hypersonic test facilities provide a test time of the order of a millisecond, which is inevitable considering the thermal and shear loads on the test models otherwise.…”

Section: Introductionmentioning

confidence: 99%

A skin-friction balance for shock tunnel applications

Kshetrimayum¹,

Menezes²,

Yerramalli³

2021

Meas. Sci. Technol.

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An acceleration-compensated skin-friction balance based on the floating-head technique was developed to measure skin friction in a hypersonic impulse facility. The balance consisted of measurement and acceleration units, the outputs of which can be coupled using a full-Wheatstone bridge to obtain pure shear output. The working of the balance was tested on a flat plate model exposed to a laminar flow with Mach number, stagnation enthalpy and Reynolds number of 8.2, 0.65 MJ kg−1 and 2.9 × 106 m−1, respectively. The measured wall shear stress agreed reasonably well with that predicted by Reynolds analogy.

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Shock tunnel measurements of surface pressures in shock induced separated flow field using MEMS sensor array

Cited by 10 publications

References 28 publications

A review of principles of MEMS pressure sensing with its aerospace applications

A review of principles of MEMS pressure sensing with its aerospace applications

Simultaneous measurement of pressure and temperature in a supersonic ejector using FBG sensors

A skin-friction balance for shock tunnel applications

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